EP2678222B1 - Système d'amortisseur à double série - Google Patents

Système d'amortisseur à double série Download PDF

Info

Publication number
EP2678222B1
EP2678222B1 EP11864375.8A EP11864375A EP2678222B1 EP 2678222 B1 EP2678222 B1 EP 2678222B1 EP 11864375 A EP11864375 A EP 11864375A EP 2678222 B1 EP2678222 B1 EP 2678222B1
Authority
EP
European Patent Office
Prior art keywords
damper
fluid
dual series
lead
lag
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP11864375.8A
Other languages
German (de)
English (en)
Other versions
EP2678222A4 (fr
EP2678222A1 (fr
Inventor
Mithat Yuce
David A. Popelka
Frank B. Stamps
Mark A. Wiinikka
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Bell Helicopter Textron Inc
Original Assignee
Bell Helicopter Textron Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Bell Helicopter Textron Inc filed Critical Bell Helicopter Textron Inc
Publication of EP2678222A4 publication Critical patent/EP2678222A4/fr
Publication of EP2678222A1 publication Critical patent/EP2678222A1/fr
Application granted granted Critical
Publication of EP2678222B1 publication Critical patent/EP2678222B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/51—Damping of blade movements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F13/00—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs
    • F16F13/04—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs comprising both a plastics spring and a damper, e.g. a friction damper
    • F16F13/06—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs comprising both a plastics spring and a damper, e.g. a friction damper the damper being a fluid damper, e.g. the plastics spring not forming a part of the wall of the fluid chamber of the damper

Definitions

  • the system of the present application relates to a damper for an aircraft.
  • the system of the present application relates to a lead/lag damper for a rotorcraft.
  • Certain rotorcraft have multi-bladed rotor hub configurations that require lead/lag dampers to compensate for the acceleration and deceleration of each rotor blade about a rotor blade hinge axis.
  • unequal drag forces on the advancing and retreating rotor blade positions typically cause oscillating forces that if left untreated, negatively affect the rotorcraft.
  • untreated lead/lag oscillating forces severely limit the life of structural components through fatigue.
  • untreated lead/lag oscillating forces have even been known to cause catastrophic results in a "ground resonance" phenomenon in which the oscillation frequency is similar to the resonant frequency of the aircraft on its landing gear.
  • lead/lag dampers are used to treat lead/lag oscillatory forces.
  • considerably shortcomings in conventional lead/lag dampers remain.
  • a rotor hub 101 for a rotorcraft includes a plurality of rotor blades 103 coupled to a central yoke 109, via a rotor grip 107.
  • Yoke 109 is coupled to a rotor mast 105 such that rotation of rotor mast 105, in a direction 113, causes the yoke 109 and rotor blades 103 to rotate about the rotor mast axis of rotation.
  • the pitch of each rotor blade 103 is selectively controlled in order to selectively control direction, thrust, and lift of the rotorcraft.
  • Each rotor blade 103 is preferably hinged about a hinge axis 111.
  • Hinge axis 111 can be the result of a discreet hinge, or alternatively from a virtual hinge.
  • a dual series damper 501 is coupled between each rotor blade 103 and the rotor yoke 109. Dual series damper 501 is configured to dampen lead/lag oscillations during operation of the rotorcraft, as further described herein. It should be appreciated that the even though rotor hub 101 is illustrated with four rotor blades 103, the system of the present application is equally applicable to rotor hubs having an alternative number of rotor blades 103.
  • rotor hub 101 is further illustrated. For clarity, only a single rotor blade 103 is shown; however, it should be appreciated that the discussion regarding the rotor blade 103 is equally applicable to other rotor blades 103 that are not shown for clarity.
  • rotor hub 101 is subjected to a variety of aerodynamic forces, as well as mechanical dynamic forces.
  • Rotor hub 101 rotates around the rotor mast axis at approximately 300-350 revolutions per minute (RPM).
  • RPM revolutions per minute
  • the rate of rotation of rotor hub 101 is implementation specific; accordingly, the system of the present invention contemplates rotor hubs that rotate at other RPM's as well.
  • a centrifugal force 119 acts upon rotor blade 103 when rotor blade 103 is rotating around the rotor mast axis. Further, an aerodynamic drag force 117 imparts a restraining force upon the rotor blade 103. The centrifugal force 119 and aerodynamic drag force 117 create moments that act upon rotor blade 103. When the moments from the centrifugal force 119 and aerodynamic drag force 117 are balanced, then the rotor blade 103 is an equilibrium position, such as equilibrium position 115.
  • rotor blade 103 is shown in a forward position 115' in which the position of rotor blade 103 has deviated forwardly from equilibrium position 115.
  • rotor blade 103 is shown in an aft position 115" in which the position of rotor blade 103 has deviated aft of equilibrium position 115.
  • an increase or decrease in aerodynamic drag can be the result of a change in the pitch angle of the rotor blade 103, thereby causing a steady force to reposition rotor blade 103 to forward position 115' or aft position 115".
  • An increase in pitch angle of rotor blade 103 increases profile drag on the rotor blade 103, whereas a decrease in pitch angle of rotor blade 103 decreases profile drag on the rotor blade 103.
  • Deviations from equilibrium position 115 can be the result of a high frequency oscillatory force acting upon rotor blade 103, such as a lead/lag force.
  • a high frequency oscillatory force acting upon rotor blade 103 such as a lead/lag force.
  • the deviation of rotor blade 103 into a forward position 115a or an aft position 115b can be the result of a lead/lag force that imparts a high frequency oscillatory force facilitating the temporary positioning of rotor blade 103 in forward position 115a or aft position 115b.
  • Dual series damper 501 includes a fluid damper portion 503 and an elastomeric damper portion 505.
  • Fluid damper portion 503 includes a first connection member 511 coupled to a piston 517.
  • the piston 517 acts to divide a cylinder portion of the housing into a first fluid chamber 523 and a second fluid chamber 525, which are in fluid communication via one or more fluid passages 519a and 519b.
  • a fluid 521 is located within first fluid chamber 523 and second fluid chamber 525.
  • Fluid 521 is preferably a hydraulic fluid, but fluid 521 can be a variety of fluid types.
  • Seals 527 and 529 act to prevent fluid 521 from leaking out of the first fluid chamber 523 and second fluid chamber 525. Further, seals 527 and 529 are preferably sliding seals that allow a shaft portion of piston 517 to slide relative to a cylinder portion of first housing 507 while preventing the leakage of fluid 521. A seal 531 creates a sliding seal to keep fluid communication between first fluid chamber 523 and second fluid chamber 525 through fluid passages 519a and 519b.
  • Dual series damper 501 also includes an elastomeric damper portion 505.
  • Elastomeric damper portion 505 includes a second connection member 513 coupled to a second housing 509.
  • An elastomer portion 515 is coupled to an interior of second housing 509 and to an exterior of a central portion of first housing 507.
  • elastomer portion 515 is adhesively bonded to the interior of second housing 509 and the exterior of the central portion of first housing 507. It should be appreciated that elastomer portion 515 may have a wide variety of configurations to tailor stiffness and damping properties. For example, one or more openings may be located in and around elastomer portion 515.
  • elastomer portion 515 may be a solid elastomer member or a laminate of elastomer layers. Further, the laminate of elastomeric layers can include cylindrically shaped shims bonded therebetween. Further, the requisite length and thickness of elastomer portion 515 is implementation specific and depends in part on the predicted rotor hub and blade loads. The geometry and composition of elastomer portion 515 may be configured to provide linear or nonlinear strain properties.
  • first connection member 511 and the second connection member 513 is coupled to the rotor yoke 109, while the other of the first connection member 511 and the second connection member 513 is coupled to the rotor grip 107 of rotor blade 103.
  • the dual series damper 501 may be associated with the rotor hub 101 in a variety of configurations.
  • dual series damper 501 may alternatively be coupled between adjacent rotor blades 103, instead of being coupled between the rotor blade 103 and rotor yoke 109.
  • first and second connection members 511 and 513 are rod ends having an integral spherical bearing; however, it should be appreciated that first and second connection members 511 and 513 may be of any configuration capable of providing a structural connection between rotor blade 103 and rotor yoke 109.
  • the fluid damper portion 503 of dual series damper 501 is configured to be rigid when subjected to a high frequency oscillatory force, such as a lead/lag force.
  • the lead/lag oscillatory forces act to generate an oscillatory lead/lag motion of rotor blade103 at a lead/lag frequency mode.
  • the elastomer damper portion 505 is to treat both the oscillatory lead/lag motion and the lead/lag frequency mode.
  • the fluid damper portion 503 is configured to be rigid at frequencies of the lead/lag frequency mode and higher, thereby obligating the elastomer damper portion 505 to endure, thus treat oscillatory lead/lag motion and the lead/lag frequency mode.
  • the fluid damper portion 503 accomplishes a rigid reaction to the oscillatory lead/lag motion through the sizing of first housing 507, piston 517, and fluid passages 519a and 519b.
  • the fluid portion 503 essentially hydrolocks so that the oscillatory lead/lag forces are rigidly transferred between first connection member 511 and first housing 507.
  • the fluid passages 519a and 519b are sized relatively small so that little or no fluid 521 is able to travel through fluid passages 519a and 519b when piston 517 is subjected to a lead/lag oscillatory force.
  • piston 517 translates relative to first housing 507 with the gradual flow of fluid 521 between first fluid chamber 523 and second fluid chamber 525 through fluid passages 519a and 519b.
  • the elastomeric damper portion 505 When dual series damper 501 is subjected to an oscillatory lead/lag motion, thereby producing a rigid reaction from the fluid damper portion 503, the elastomeric damper portion 505 is configured to treat the oscillatory lead/lag motion and the lead/lag frequency mode. More specifically, the spring function of the elastomeric portion 505 is configured to treat the lead/lag mode frequency of the rotor blade 103. For example, the spring function of the elastomeric portion 505 can transform a 1 per revolution lead/lag frequency to a frequency range between 0.4 and 0.75 per revolution. It should be appreciated that the spring constant of the elastomeric portion 505 can be specifically configured to transform the lead/lag frequency into a variety of selected frequencies.
  • the dampening function of the elastomeric portion 505 is configured to dampen the oscillatory lead/lag motion of the rotor blade 103 at the lead/lag mode frequency and higher.
  • Elastomeric portion 505 achieves damping of the lead/lag mode frequencies via shearing deformation of elastomer 515.
  • a length L1 corresponds with a length of dual series damper 501 while rotor blade 103 is in equilibrium position 115.
  • Equilibrium position 115 represents the position of rotor blade 103 in a normal or average position based up predicted flight regimes.
  • the fluid damper portion 503 and the elastomeric damper portion 505 are each in a central position. More specifically, piston 517 is located centrally in the cylinder portion of first housing 507, while elastomer 515 is in an undeformed state between the central portion of first housing 507 and second housing 509.
  • a length L2 and positioning of fluid damper portion 503 are indicative of dual series damper 501 of being compressed from equilibrium position 115 to aft position 115" as the result of being subjected to a steady force.
  • the steady force acts to translate piston 517 until the fluid pressures in first fluid chamber 523 and second fluid chamber 525 are equalized.
  • the steady force acts on dual series damper 501 to reposition rotor blade 103 from equilibrium potion 115 to aft position 115" so that aft position 115" becomes the new stabilized blade position.
  • the rotor blade 103 is in a new stabilized blade position such that the steady force is zero.
  • a length L3 and positioning of fluid damper portion 503 are indicative of dual series damper 501 of being stretched from equilibrium position 115 to forward position 115' as the result of being subjected to a steady force.
  • the steady force acts to translate piston 517 until the fluid pressures in first fluid chamber 523 and second fluid chamber 525 are equalized.
  • the steady force acts on dual series damper 501 to reposition rotor blade 103 from equilibrium position 115 to forward position 115' so that forward position 115' becomes the new stabilized blade position.
  • the rotor blade 103 is in a new stabilized blade position such that the steady force is zero.
  • a steady force is fully eliminated by the fluid damper portion 503 of the dual series damper 501.
  • One significant advantage of this feature is that without fluid damper portion 503, the elastomer damper portion 505 would have to endure the steady force.
  • One shortcoming of elastomer material is that it is susceptible to creep, in which a steady force causes continual deflection over time, even when the steady force doesn't change.
  • the magnitude of creep on each elastomer damper may typically be different for each damper on a particular rotor hub. As such, the creep differential on each elastomer damper could cause each rotor blade to be located in different position, thus causing an out-of-position vibration inducing scenario.
  • dual series damper 501 is configured to prevent creep of elastomer 515 by preventing the elastomer damper portion 505 from being subjected to steady forces. Furthermore, dual series damper 501 is configured to passively adjust the length L1 in order to compensate for changes in equilibrium position 115 due to steady forces induced by a change in a flight regime of the rotorcraft.
  • a variable rpm rotorcraft can be configured such that the rotor hub 101 can rotate around the rotor hub 101 at different RPM's. Each rotor hub RPM will typically correspond with a slightly different equilibrium position 115 of the rotor blades 103.
  • dual series damper 501 is particularly well suited for variable rpm rotorcraft because the fluid damper portion 503 eliminates the steady forces by changing the damper length, such as damper length L1. Furthermore, this prevents creep induced misalignment of the rotor blades, due to the absence of the steady force, while also preserving elastomer damper portion 505 for treatment of the oscillatory lead/lag motion and the lead/lag frequency mode.
  • a length L4 and positioning of elastomeric damper portion 505 are indicative of dual series damper 501 being stretched from equilibrium position 115 to forward position 115a as the result of being subjected to a lead/lag oscillatory motion.
  • the lead/lag oscillatory motion acts to translate the central portion of first housing 507 relative to second housing 509, thereby deforming elastomer 515 so as to treat the lead/lag oscillatory motion and the lead/lag frequency mode.
  • a length L5 and positioning of elastomeric damper portion 505 are indicative of dual series damper 501 being compressed from equilibrium position 115 to aft position 115b as the result of being subjected to a lead/lag oscillatory motion.
  • the lead/lag oscillatory motion acts to translate the central portion of first housing 507 relative to second housing 509, thereby deforming elastomer 515 so as to treat the lead/lag oscillatory motion and the lead/lag frequency mode.
  • Dual series damper 1101 is similar to dual series damper 501 except that sliding seals 527 and 529 are replaced with elastomeric membranes 1127 and 1129, respectively. It should also be appreciated that seal 531 may also be replaced with an elastomeric membrane similar to membranes 1127 and 1129.
  • Membranes 1127 and 1129 are bonded to first housing 507 and piston 511. Deflection of membranes 1127 and 1129 allow piston 511 to translate relative to first housing 507 while preventing undesired leakage of fluid 521.
  • dual series damper 1101 may be preferred because elastomer membranes may provide better reliability than sliding seals.
  • Dual series damper 1201 is similar to dual series damper 501 except that sliding seal 531 on piston 517 is not used. Rather, a gap 1203 between a circumferential surface of piston 517 and an interior surface of first housing 507 replaces the fluid passages 519a and 519b of dual series damper 501. As such, gap 1203 functions similar to fluid passages 519a and 519b of dual series damper 501.
  • the system of the present application provides significant advantages, including: (1) providing a dual series damper that prevents creep of an elastomer, thus increasing rotor blade position uniformity; and (2) providing a dual series damper that passively changes length when subjected to a steady force.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluid-Damping Devices (AREA)
  • Vibration Dampers (AREA)

Claims (16)

  1. Un amortisseur double (501, 1102, 1201) pour un giravion, l'amortisseur double comprenant :
    une partie amortisseur à fluide (503) comprenant :
    un premier logement (507),
    un premier élément de raccordement (511),
    un piston (517), le piston divisant un intérieur du premier logement en une première chambre à fluide (523) et une deuxième chambre à fluide (525),
    un passage de fluide (519a, 519b, 1203) dans le piston, le passage de fluide étant configuré de façon à fournir une communication fluidique entre la première chambre à fluide et la deuxième chambre à fluide,
    une partie amortisseur élastomère (505) comprenant :
    un deuxième logement (509),
    un deuxième élément de raccordement (513) couplé au deuxième logement,
    un élastomère (515) entre le premier logement et le deuxième logement caractérisé en ce que :
    le piston (517) est couplé au premier élément de raccordement,
    et en ce que
    la partie amortisseur élastomère se déplace indépendamment de la partie amortisseur à fluide.
  2. Un moyeu de rotor (101) pour un aéronef, le moyeu de rotor comprenant :
    une cardan de rotor (109),
    une pluralité de poignées de pale (107) couplées au cardan de rotor,
    une pale de rotor (103) couplée à chaque poignée de pale, et
    un amortisseur double selon la Revendication 1 couplé entre chaque poignée de pale et le cardan de rotor.
  3. L'amortisseur double selon la Revendication 1, où la partie amortisseur à fluide (503) est configurée de façon à se comporter de manière rigide lorsque l'amortisseur double est soumis à une force d'oscillation d'avance/recul, ou
    le moyeu de rotor selon la Revendication 2 où la partie amortisseur à fluide (503) de l'amortisseur double est configurée de façon à se comporter de manière rigide lorsque l'amortisseur double est soumis à une force d'oscillation d'avance/recul à un mode de fréquence d'avance/recul et supérieur.
  4. L'amortisseur double selon la Revendication 1, où la partie amortisseur élastomère (505) est configurée de façon à amortir un mouvement d'oscillation d'avance/recul et également à fournir une force de rappel qui ajuste une fréquence en mode avance/recul sur une valeur souhaitée, ou
    le moyeu de rotor selon la Revendication 2, où la partie amortisseur élastomère (505) de l'amortisseur double est configurée de façon à amortir une oscillation d'avance/recul et à fournir une force de rappel à un mode de fréquence d'avance/recul.
  5. L'amortisseur double selon la Revendication 1, où la partie amortisseur à fluide est configurée de sorte que le passage de fluide (519a, 519b, 1203) permette à un fluide de circuler entre la première chambre à fluide (523) et la deuxième chambre à fluide (525) lorsque l'amortisseur double est soumis à une force constante, ou
    le moyeu de rotor selon la Revendication 2, où la partie amortisseur à fluide de l'amortisseur double est configurée de sorte que le passage de fluide (519a, 519b, 1203) permette à un fluide de circuler entre la première chambre à fluide (525) et la deuxième chambre à fluide (525) lorsque l'amortisseur double est soumis à une force constante.
  6. L'amortisseur double selon la Revendication 1, où la partie amortisseur à fluide (503) est configurée de façon à se comporter de manière rigide lorsque l'amortisseur double est soumis à une force se produisant à une fréquence en mode avance/recul.
  7. L'amortisseur double selon la Revendication 1, où l'amortisseur double est configuré de façon à être fixé entre une pale de rotor (103) et un cardan de rotor (109), ou où l'amortisseur double est configuré de façon à être fixé entre des pales de rotor adjacentes (103).
  8. L'amortisseur double selon la Revendication 1, où la partie amortisseur élastomère (505) est configurée de façon à amortir un mouvement d'oscillation d'avance/recul et à fournir une force de rappel destinée à ajuster une fréquence en mode avance/recul par l'intermédiaire d'une déflexion de l'élastomère.
  9. L'amortisseur double selon la Revendication 1, où le premier logement possède une partie cylindre et une partie centrale, et
    où la partie amortisseur élastomère est configurée de façon à amortir un mouvement d'oscillation, tandis que la partie amortisseur à fluide est configurée de façon à supprimer une force constante.
  10. L'amortisseur double selon la Revendication 9, où le mouvement d'oscillation se produit à une fréquence en mode avance/recul et supérieur.
  11. L'amortisseur double selon la Revendication 9, où l'élastomère de la partie amortisseur élastomère possède une rigidité suffisante pour traiter le mouvement d'oscillation.
  12. L'amortisseur double selon la Revendication 9, la partie amortisseur à fluide comprenant en outre :
    un joint d'étanchéité coulissant (527, 529) entre le piston et la partie cylindre du premier logement.
  13. L'amortisseur double selon la Revendication 9, la partie amortisseur à fluide comprenant en outre :
    un joint d'étanchéité élastomère (1127, 1129) entre le piston et la partie cylindre du premier logement.
  14. L'amortisseur double selon la Revendication 9, où la partie amortisseur à fluide est configurée de façon à modifier de manière passive la longueur de l'amortisseur double lorsqu'il est soumis à la force constante.
  15. L'amortisseur double selon la Revendication 9, où la partie amortisseur à fluide est configurée de façon à modifier de manière passive la longueur de l'amortisseur double lorsqu'il est soumis à la force constante par l'intermédiaire d'une translation du piston par rapport à la partie cylindre du premier logement.
  16. Le moyeu de rotor selon la Revendication 2, où la partie amortisseur à fluide se comporte de manière rigide lorsqu'une force d'oscillation d'avance/recul est introduite dans l'amortisseur double, de sorte que la partie amortisseur élastomère traite la force d'oscillation d'avance/recul.
EP11864375.8A 2011-04-26 2011-04-26 Système d'amortisseur à double série Active EP2678222B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2011/033956 WO2012148389A1 (fr) 2011-04-26 2011-04-26 Système d'amortisseur à double série

Publications (3)

Publication Number Publication Date
EP2678222A4 EP2678222A4 (fr) 2014-01-01
EP2678222A1 EP2678222A1 (fr) 2014-01-01
EP2678222B1 true EP2678222B1 (fr) 2014-09-24

Family

ID=47072629

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11864375.8A Active EP2678222B1 (fr) 2011-04-26 2011-04-26 Système d'amortisseur à double série

Country Status (5)

Country Link
US (1) US9481455B2 (fr)
EP (1) EP2678222B1 (fr)
CN (1) CN103476672B (fr)
CA (1) CA2831584C (fr)
WO (1) WO2012148389A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11161601B2 (en) 2018-03-30 2021-11-02 Airbus Helicopters Hydro-elastic damper and an aircraft
US11518503B2 (en) 2018-05-31 2022-12-06 Airbus Helicopters Hydroelastic damper, and an aircraft

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2895491C (fr) 2012-12-21 2017-07-11 Bell Helicopter Textron Inc. Systeme et procede pour ajustement de la longueur de la tringlerie
US9656747B2 (en) * 2013-03-14 2017-05-23 Bell Helicopter Textron Inc. Soft in-plane and stiff out-of-plane rotor system
US10583920B2 (en) 2013-04-02 2020-03-10 Hood Technology Corporation Multicopter-assisted system and method for launching and retrieving a fixed-wing aircraft
US10569868B2 (en) * 2013-04-02 2020-02-25 Hood Technology Corporation Multicopter-assisted system and method for launching and retrieving a fixed-wing aircraft
WO2015066397A1 (fr) * 2013-10-31 2015-05-07 Lord Corporation Dispositif systèmes et procédés de réglage du pas dynamique
FR3040042B1 (fr) * 2015-08-14 2018-06-01 Airbus Helicopters Dispositif d'amortissement, et aeronef
US10494111B2 (en) * 2015-09-14 2019-12-03 Lord Corporation Aircraft support structures, systems, and methods
US20180162526A1 (en) * 2016-12-12 2018-06-14 Bell Helicopter Textron Inc. Proprotor Systems for Tiltrotor Aircraft
US10689104B2 (en) 2017-05-09 2020-06-23 Textron Innovations Inc. Tail rotor integrated damper attachment
CN109268426B (zh) * 2018-11-15 2019-10-18 中国直升机设计研究所 一种反共振频率可调的液压式动力反共振隔振器
FR3090777B1 (fr) 2018-12-19 2022-04-08 Airbus Helicopters Amortisseur hydroelastique, rotor comportant un tel amortisseur hydroelastique et aeronef associe
US11235892B2 (en) 2019-05-22 2022-02-01 Hood Technology Corporation Aircraft retrieval system and method

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4105365A (en) 1976-10-04 1978-08-08 United Technologies Corporation Helicopter rotor lead-lag damper
FR2592696B1 (fr) * 1986-01-09 1989-12-01 Aerospatiale Contre-fiche de rappel elastique a amortissement incorpore, de type hydro-elastique.
FR2659710B1 (fr) * 1990-03-13 1994-08-26 Aerospatiale Amortisseur hydraulique et contre-fiche de rappel elastique comportant un tel amortisseur.
US5501434A (en) 1994-05-10 1996-03-26 Lord Corporation Hybrid fluid and elastomer damper
US6092795A (en) 1997-08-04 2000-07-25 Lord Corporation Fluid and elastomer damper
US6045328A (en) 1998-09-23 2000-04-04 Lord Corporation Fluid damper including flexible damping plate
DE10001159A1 (de) 2000-01-13 2001-07-26 Liebherr Aerospace Gmbh Schwingungsisolator für Helikopter
US8038394B2 (en) * 2008-01-16 2011-10-18 Sikorsky Aircraft Corporation System and method of damping a 1P motion
PL2223854T3 (pl) 2009-02-25 2011-11-30 Agustawestland Spa Wirnik Śmigłowca
WO2010129322A1 (fr) * 2009-04-28 2010-11-11 Lord Corporation Ensemble amortisseur élastomère à fluide

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11161601B2 (en) 2018-03-30 2021-11-02 Airbus Helicopters Hydro-elastic damper and an aircraft
US11518503B2 (en) 2018-05-31 2022-12-06 Airbus Helicopters Hydroelastic damper, and an aircraft

Also Published As

Publication number Publication date
EP2678222A4 (fr) 2014-01-01
WO2012148389A1 (fr) 2012-11-01
EP2678222A1 (fr) 2014-01-01
CN103476672A (zh) 2013-12-25
CN103476672B (zh) 2015-03-25
US9481455B2 (en) 2016-11-01
CA2831584A1 (fr) 2012-11-01
CA2831584C (fr) 2014-12-09
US20130084183A1 (en) 2013-04-04

Similar Documents

Publication Publication Date Title
EP2678222B1 (fr) Système d'amortisseur à double série
US7828525B2 (en) Soft in-plane tiltrotor hub
CA2805894C (fr) Amortisseur a deux frequences pour aeronef
CA2863707C (fr) Amortisseur de moyeu de rotor pour un giravion
EP2223854B1 (fr) Rotor d'hélicoptère
EP2686239B1 (fr) Moyeu de rotor destiné à être utilisé avec des pales à inertie élevée
EP2665945B1 (fr) Système d'amortissement utilisant un fluide s'adaptant à la température
US8579587B2 (en) Method of reducing or even eliminating the vibration of a rotorcraft lift and propulsion rotor, and an airfoil assembly and a rotor implementing said method
US20140271180A1 (en) Gimbaled Tail Rotor Hub with Spherical Elastomeric Centrifugal Force Bearing for Blade Retention and Pitch Change Articulation
US20180093764A1 (en) Articulated Main Rotor Hub with Inwardly CF Bearing and 3% Flapping Hinge Offset
EP3755623A1 (fr) Moyeu de rotor
US8297928B2 (en) Blade for reducing the drag movements of said blade, and a method of reducing such a drag movement
US9988146B2 (en) Rotor balancing apparatus
CA3017372A1 (fr) Moyeu de rotor a amortisseurs aube-aube et roulements a rotule elastomeres a symetrie axiale
US11203418B2 (en) Mount systems for pylon assemblies with coaxial rotors
EP2554476B1 (fr) Amortisseur de traînée pour unité de rotor d'hélicoptère
US20150132131A1 (en) Rotor balancing apparatus
KR20230072781A (ko) 로터 허브 시스템의 다이나믹 댐핑 스토퍼 조립체

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20130926

A4 Supplementary search report drawn up and despatched

Effective date: 20131115

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

DAX Request for extension of the european patent (deleted)
GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

INTG Intention to grant announced

Effective date: 20140725

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 688492

Country of ref document: AT

Kind code of ref document: T

Effective date: 20141015

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602011010190

Country of ref document: DE

Effective date: 20141106

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141225

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20141224

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20140924

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 688492

Country of ref document: AT

Kind code of ref document: T

Effective date: 20140924

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150126

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150124

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602011010190

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20150625

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150426

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150430

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150426

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20110426

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140924

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230602

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230419

Year of fee payment: 13

Ref country code: FR

Payment date: 20230425

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240429

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240429

Year of fee payment: 14